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see also wings
airplane response, 537
see abo lareral-directional response;
longitudinal response
altitude, 108, 109, 1{0, 111-113
altitude-hold autopilor, 616-622
angle of attack
definition, 2
roll angle and, 695, 696
sideslip and, 695, 696
wing rock and, 695-710
see also high angles of attack
Angla-French Concorde, 55, 208
angular momentum, 368~372
area ruling, 59-60
aspect ratio, 45, 46, 299-304
asymmetric power, 281, 283
759
asymmetr:ic stall, 646
asymptotes, 470
attached flow, 676
Index
autopilots, 563, 588, 595, 61 J -622
autorotation characteriscics, 640-645
autothrottle, 157
axes systems
body axes, 321-322, 328-330, 336-337
Earth fixed, 321-322
inertial, 320, 326-328
nayigational, 321, 334-337
overview, 320
axes transformation
direction cosine matrix, 337-344
Euler an. gles, 322-337
quatemoins, 344-347
B
B*,l aircraft, 50, 60, 106
B-52 aircraft, 106, 234
balanced field length, 151
bank angle, 124, 570, 572
BemouIJi's theOfem. 6
Bode plot, 483
body axes system, 321-322. 328-330,
336-337
Boeing 707 aircraft, 234
Boeing 747 aircraft, 60, 106
Boeing 747-400 aircraft, 32
Boeing 757 aircrafi, 34
boundary layer, 42, 53
circular cylindef fluid flow and, 7-li
control of, 26
fluid flow and, 2-7
Breguet range formula, 109, 113
Bryan, G. H., 319, 376
buffeting, 42, 674
Busemann's supersonic swept-wing
theory, 47
C
C-I40 JetStar airCfafi, 26
canard aircraft, 174, 205, 689
canard deflector, 689-690
center of gravity
effect on longitudinaJ response, 555-556
elevator deflection and, 213
most forwafd location of, 213-2 ! 4
permissible, 214-215
shift in, 208
stability and, 201-203
stick-free margin. 228
chordline, 12- 13, 17, 20
760
INDEX
circular cylinder
drag af bodies and, 12
fluid velocity and, 2-3, 7-11
pressure disrribution over, 9-10
circulation control, 26
climbing flight
absolute ceiling, 99-100
aircraft performance, 104 .
energy climb method, 100-104
jet aircraft, 97-99, 101-102
propeller aircraft, 95-97
service ceiling, 99-100
steady climb, 94-99
subsonic aircraft, 102
supersonic aircraft, 102~104
close-coupled canards, 689
closed-loop systems, 439, 537 '
autopilots, 563, 588, 595, 611-622
full-state feedback, 599-604, 607-611
gain margin, 481-483
Nyquist srability cn:terion, 473-478
overview, 595-596
phase margin, 481-483
pitch stabilization, 596-600
root-locus method, 467-470
Routh's stability criterion, 463-465
stability of, 461-465
yaw damper, 604-607
Coanda effect, 725
combat aircraft, 136-137
compensators
design, 487-488
lead/lag, 492
overview, 486-488
proportional-derivative, 490-491
proportional-integral, 488-490
compressibility, 19, 45-59
computational fluid dynamics (CFD), 389-390
cone-cylinders, 173-174
coning motion, I39
constant ampWude sinusoid, 448
constant-alritude flight, 113, t 15-116
constant-velocity flighr, I J 0, 113, 115-116
controllability matrix, 5 12
controller, proportional-integral and derivative,
492-493
Convair B-58 aircraft, 60
Convair F- 102 aircraft, 59-60
Convair F-I06 aircraft, 60
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PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL4(109)
